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کنترل تحملپذیر عیب فعال فضاپیمای انعطافپذیر با استفاده از مشاهدهگر تطبیقی مبتنیبر شبکه عصبی توابع پایه شعاعی | ||
| مکانیک هوافضا | ||
| مقاله 3، دوره 21، شماره 2 - شماره پیاپی 80، تیر 1404، صفحه 37-52 اصل مقاله (1.48 M) | ||
| نوع مقاله: گرایش دینامیک، ارتعاشات و کنترل | ||
| شناسه دیجیتال (DOI): 10.47176/MAJ.2025.1476 | ||
| نویسندگان | ||
| مرضیه اقلیمی دژ1؛ میلاد عظیمی* 2؛ علیرضا علیخانی2 | ||
| 1کارشناسی ارشد، پژوهشگاه هوافضا (وزارت علوم، تحقیقات و فناوری)، تهران، ایران | ||
| 2دانشیار، پژوهشگاه هوافضا (وزارت علوم، تحقیقات و فناوری)، تهران، ایران | ||
| تاریخ دریافت: 04 اردیبهشت 1404، تاریخ بازنگری: 12 خرداد 1404، تاریخ پذیرش: 21 خرداد 1404 | ||
| چکیده | ||
| در این مقاله به طراحی و توسعه الگوریتم کنترل تحملپذیر عیب مود لغزشی و مشاهدهگر تطبیقی، جهت مقابله با نامعینیهای سیستم، عیب عملگر و اغتشاشات خارجی برای یک فضاپیمای انعطافپذیر پرداخته شده است. جهت تخمین عیب عملگرهای وضعیت، یک مشاهدهگر تطبیقی مبتنی بر شبکه عصبی طراحی شده است. عملکرد این مشاهدهگر با یک مشاهدهگر یادگیری تکرارشونده مقایسه شده است. کنترل تحمل پذیر عیب پیشنهادی از یک سطح لغزش PID جهت افزایش عملکرد، قوام و پاسخ زمانی سریع برای یک فضاپیمای انعطاف پذیر با عیب عملگر بهره میبرد. علاوهبراین، الگوریتم کنترل فعال ارتعاشات فیدبک نرخ کرنش جهت کاهش موثر ارتعاشات با استفاده از عملگرها و حسگرهای پیزوالکتریک نیز طراحی شده است. پایداری سیستم حلقه بسته با استفاده از قضیه لیاپانوف مورد بررسی قرار گرفته است. یکی از ویژگیهای کلیدی رویکرد پیشنهادی، سادگی آن و همچنین توانایی آن جهت پایدارسازی سیستم با در نظر گرفتن خطا و توانایی تخمین عیب عملگر با حداقل بار محاسباتی است. شبیهسازیها در قالب یک مطالعه مقایسه ای، عملکرد، قوام و تحمل پذیری عیب رویکرد پیشنهادی، برای یک سیستم با دینامیک کاملا کوپل صلب انعطاف پذیر را نمایش میدهد. | ||
| کلیدواژهها | ||
| دینامیک صلب-انعطافپذیر؛ شبکه عصبی توابع پایه شعاعی؛ کنترل تحملپذیر عیب مود لغزشی؛ کنترل فعال ارتعاشات؛ فضاپیمای انعطافپذیر؛ مشاهدهگر عیب عملگر تطبیقی | ||
| عنوان مقاله [English] | ||
| Active Fault-Tolerant Sliding Mode Control of Flexible Spacecraft Using Adaptive Observer Based on Radial Basis Functions Neural Network | ||
| نویسندگان [English] | ||
| Marzieh Eghlimi Dezh1؛ Milad Azimi2؛ Alireza Alikhani2 | ||
| 1Master's degree, Aerospace Research Institute (Ministry of Science, Research and Technology), Tehran, Iran | ||
| 2Associate Professor, Aerospace Research Institute (Ministry of Science, Research and Technology), Tehran, Iran | ||
| چکیده [English] | ||
| This paper is focused on the design and analysis of a fault-tolerant sliding mode control algorithm together with an adaptive observer for applications to a flexible spacecraft in order to attenuate system uncertainties, actuator faults, and external disturbances. For estimation of the actuator faults, an adaptive observer is designed using a radial basis function neural network, whose performance is compared with an iterative learning observer. The proposed fault-tolerant control adopts a PID sliding surface for high performance, robustness, and fast response. Additionally, the vibration suppression control algorithm based on strain rate feedback was designed for active suppression of structural vibrations using piezoelectric actuators and sensors. Stability analysis of the closed-loop system is performed using the Lyapunov theorem to ensure its robust performance. A key feature of the proposed approach is its simplicity and its ability to stabilize the system under fault conditions while providing accurate actuator fault estimation with minimal computational burden. Simulations, presented as a comparative study, demonstrate the superior performance, robustness, and fault-tolerance of the proposed approach for a system with fully coupled rigid-flexible dynamics. | ||
| کلیدواژهها [English] | ||
| Rigid-flexible dynamics, Radial basis function neural network, Sliding mode fault-tolerant control, Active vibration control, Flexible spacecraft, Adaptive actuator fault observer | ||
| مراجع | ||
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آمار تعداد مشاهده مقاله: 3,410 تعداد دریافت فایل اصل مقاله: 62 |
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